Alloys



3,220,808 ALLOYS John Elvet Davies, London, England, assignor to Bristol 3,220,808 Patented Nov. 30, 1965 "ice this alloy melts at 715 C. and flows readily in an argon atmosphere at 720 C.

Example 2 2 3 3; E g Limited, Bristol, England, 8 company 5 Hylite 50 and I.M.I. Titanium 679 are creep-resistant, 0 Tea am hi h-tensile titanium alloys and are in consequence used No Drawing. Filed .lune 28 1963 Sex. No. 291 283 I 0 Claims priority application a Britain June 1962 1n compressors at temperatures in the range 300 to 450 C.

25 90/62 The heat treatment of these alloys is preferably performed 9 (6L 29 194) at 900 C. and accordingly these can be brazed using a 10 silver aluminum alloy with 2.5% aluminum because this This invention relates to silver aluminum alloys and alloy hasameltlng P f39 one object is to provide such an alloy for use as a brazing Example 3 alloy for brazing titanium and titanium alloys.

According to the present invention an alloy Consists I.M.I. Titanium 314A and I-lyhte 40 are standard titaof from 85.1% to 99.5% of silver, the balanceexcluding mum foFgmg alloys used on alrcraft components and m impurities being substantially an aluminum gas turbine compressors. A preferred heat treatment for According to another aspect of the invention, an alloy these alloys 15 Performed at 800 P accordmgly 3 consists of from 85.1% to 99.5% of silver; and from alumlnum,auoy used as the brazing alloyfiecluse 0.5% to 14.9% of aluminum, the balance-excluding imthis has a melnng Pomt of 7900 An alternatlve to puritiesbeing well known additives used for brazing Perform the heat treaimanbat 700 anoys and perform the brazing with a 14.9% alurnmum alloy. usual additions are betwem 005% and 1% 0f1ith I.M.I. Titanium 318A and Hylite 45 are alternative alloys ium, between 0.05% and 2% of copper, between 0.05% to mennonfid m thls exampleand 2% of nickel, and between 0.05% and 2% of man- E l 4 anese. a The particular alloys defined above melt at about or t 3 4 Hyhte 20 a i t i above 700 C. and this makes them suitable for combining sheet forging t1tan1um alloys having hlgh'tensfle a titanium brazing operation with a solution treatment, properties and thefe plefera'bly treated at 3' or ageing treatment, or annealing operation, to be carried 3 32 1 2 i g 'ig i g g ig t gs s out simultaneously at a temperature above 700 C. For brizin i these tilanium 110 s y certain titanium alloys, certain specific heat treatments are g y a y desirable and these should be carried out at certain specific Example 5 temperatures and therefore brazing alloys having melting I M I Titanium 230 is a titanium alloy in sheet form oints a little below these specific temperatures may be 3 gsed. Particular alloys of this nature have respectively fl-jrgmg p which is capable (gbemg weld-ed 86% 97 5% 94% 851% and between 95 5% and 97 7% thls pgeferibly treats; at f t t t silver. The alloys, the subject of this invention, are not gig g g gf fi a ver a ummum 3; 332 i' ggggg gg gi ggg i s g pi g z If a vacuum furnace is available, the brazingoperation tio n may be considered also to include a method of brazwill preferzrbly Pa carried a m valculgm or possibly In the resence 0 an me t as. ow v r c ing titanium or a t1tan1um alloy using as a brazing alloy, available a i E ba fl a; lie i ls cl Vacuum fuma e 82123; ggg g ig ggg zzz ffi gigggg 3x 32 I The invention is expected to have particular application ticular heat treatment of the titanium or titanium alloy. alrcrafi engines and more partlcularly for bopdmg Certain specific examples of brazing alloys useful for or tltarilum alloy Compmssor blalles l their brazing particular titanium alloys requiring particular heat mg rmgs Y i may al.so b made of t1tan1um 9 tltannlm treatments are exemplified b 61 OW alloy. This is because in view of troubles experienced with corrosion of steel parts particularly in naval applications Example 1 with the more rapid rates of corrosion due to sea air, there I.M.I. Titanium 205 (EX01'1) is a titanium alloy which i a real requirement for a o s n resistant me l h vi unique i h i i bl of b i ld n d d a ing the strength of steel, and titanium and certain titanium preferred heat treatment for this alloy is performed at alloys fulfil this requirement. 725 C. For brazing this titanium alloy, 21 silver alumi- The following table gives the compositions of the varinum alloy having 14% of aluminum is preferred because ous alloys referred to above.

Alloy Al Cu Mn Mo Si Sn V Zr Remarks I.M.I. 205 (EX01 1) 15 Cold Rolled High Strength. I.M.I. 314A, Hyhte 40... 4 4 Eggings, useable up to 350 I.M.I. 318A, Hy1ite45. e 4 Forggngagd Sheetuseableup 0 I.M.I. 317, Hylite 20 5 2% Weldable Forging and Sheet useable up to 400 C. I.M.I. 230 2 Forging and Sheet stronger $121121 (ifimmercially Pure e a e. Hylite 50 4 4 2 Forging, useableup to400 C. I.M.I. 679 2% 1 .4 11 5 F0rging,useableup to450 C.

I.M.I. alloys are supplied by Imperial Metals Industries, Limited. Hylite alloys are supplied by William J essop Limited. Figures given are percentages by weight approximately. The balance is substantially all titanium.

What I claim as my invention and desire to secure by Letters Patent is:

1. A method of brazing components of a material comprising 85% titanium and 15% molybdenum in which a brazing alloy consisting of 86% silver and 14% aluminum is raised to a temperature of 725 C. to braze the components.

2. A method of brazing components of a material comprising 89.5% titanium, 4% aluminum, 4% molybdenum, 2% tin, and 0.5% silicon, in which a brazing alloy consisting of 97.5% silver, and 2.5% aluminum is raised to a temperature of 900 C. to braze the components.

3. A method of brazing components of a material comprising 80.-35% titanium, 2.25% aluminum, 1% molybdenum, 0.4% silicon, 11% tin, and 5% zirconium, in which a brazing alloy consisting of 97.5% silver, and 2.5 aluminum is raised to a temperature of 900 C. to braze the components.

4. A method of brazing components of a material comprising 92% titanium, 4% aluminum and 4% manganese, in which a brazing alloy consisting of 94% silver and 6% aluminum is raised to a temperature of 800 C. to braze the components.

5. A method of brazing components of a material comprising 90% titanium, 6% aluminum, and 4% vanadium, in which a brazing alloy consisting of 94% silver and 6% aluminum is raised to a temperature of 800 C. to braze the components.

6. A method of brazing components of a material comprising 92.5% titanium, 5% aluminum, and 2.5 tin in which a brazing alloy consisting of 97.7% to 95.5% silver and from 4.5% to 2.3% of aluminum is raised to a temperature between 850 C. and 950 C. to braze the components.

7. A method of brazing components of a material comprising 98% titanium and 2% copper in which a brazing alloy consisting of 94% silver and 6% aluminum is raised to a temperature of 800 C. to braze the components.

8. A brazed joint in which components of a material in the group comprising titanium and a titanium alloy are united by an alloy consisting of from 85.1% to 99.5% silver and from 14.9% to 0.05% aluminum.

9. A brazed joint in which components of a material in the group comprising titanium and titanium alloy are united by an alloy consisting of '85 .1% to 99.5% of silver and from 14.9% to 0.5% aluminum and at least one additive taken from the group comprising from 0.05 to 1% of lithium, from 0.05% to 2% of copper, from 0.05 to 2% of nickel, and from 0.05% to 2% of manganese.

References Cited by the Examiner UNITED STATES PATENTS 475,382 5/1892 Carroll 173 1,863,612 6/1932 Assmann 75173 1,863,645 6/1932 Assmann 75173 2,376,577 5/1945 Dean 75-173 2,376,581 5/1945 Dean 75173 2,793,115 5/1957 Bredzs 75173 2,914,848 12/1959 Blum 75173 OTHER REFERENCES Metals Handbook, 1948 edition, pages 11, 46.

DAVID L. RECK, Primary Examiner.

HYLAND BIZOT, Examiner. 

8. A BRAZED JOINT IN WHICH COMPONENTS OF A MATERIAL IN THE GROUP COMPRISING TITANIUM AND A TITANIUM ALLOY ARE UNITED BY AN ALLOY CONSISTING OF FROM 85.1% TO 99.5% SILVER AND FROM 14.9% TO 0.05% ALUMINUM. 